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2018-02-08 |
BELL HELICOPTER TEXTRON: Amendment 39-19161; Docket No. FAA-2017-0895; Product Identifier 2017-SW-048-AD. |
(a) APPLICABILITY
This AD applies to Bell Helicopter Textron (Bell) Model 204B, 205A and
205A-1 helicopters with a Helicopter Technology Company (HTC) main
rotor (M/R) blade part number 204P2100-101 installed, certificated in
any category.
(b) UNSAFE CONDITION
This AD defines the unsafe condition as a crack in an M/R blade, which
could result in failure of an M/R blade and subsequent loss of heli-
copter control.
(c) EFFECTIVE DATE
This AD becomes effective February 1, 2018.
(d) COMPLIANCE
You are responsible for performing each action required by this AD
within the specified compliance time unless it has already been accom-
plished prior to that time.
(e) REQUIRED ACTIONS
(1) Within 25 hours time-in-service (TIS) or 2 weeks, whichever occurs
first, and thereafter at intervals not to exceed 25 hours TIS or 2
weeks, whichever occurs first, clean the upper and lower exposed sur-
faces of each M/R blade from an area starting at the butt end of the
blade to three inches outboard of the doublers. Using a 3X or higher
power magnifying glass and a light, inspect as follows:
(i) Visually inspect the exposed areas of the lower grip pad and upper and
lower grip plates of each M/R blade for a crack and any corrosion.
(ii) On the upper and lower exposed surfaces of each M/R blade from blade
stations 24.5 to 35 for the chord width, visually inspect each lay-
ered doubler and blade skin for a crack and any corrosion. Pay par-
ticular attention for any cracking in a doubler or skin near or at
the same blade station as the blade retention bolt hole (blade
station 28).
(iii) Visually inspect the exposed areas of each bond line at the edges of
the lower grip pad, upper and lower grip plates, and each layered
doubler (bond lines) on the upper and lower surfaces of each M/R
blade for the entire length and chord width for an edge void, any
corrosion, loose or damaged adhesive squeeze-out, and an edge delam-
ination. Pay particular attention to any crack in the paint finish
that follows the outline of a grip pad, grip plate, or doubler, and
to any loose or damaged adhesive squeeze-out, as these may be the
indication of an edge void.
(2) If there is a crack, any corrosion, an edge void, loose or damaged ad-
hesive squeeze-out, or an edge delamination during any inspection in
paragraph (e)(1) of this AD, before further flight, do the following:
(i) If there is a crack in a grip pad or any grip plate or doubler, re-
place the M/R blade with an airworthy M/R blade.
(ii) If there is a crack in the M/R blade skin that is within maximum re-
pair damage limits repair the M/R blade. If the crack exceeds maximum
repair damage limits, replace the M/R blade with an airworthy M/R
blade.
(iii) If there is any corrosion within maximum repair damage limits, re-
pair the M/R blade. If the corrosion exceeds maximum repair damage
limits, replace the M/R blade with an airworthy M/R blade.
(iv) If there is an edge void in the grip pad or in a grip plate or
doubler, determine the length and depth using a feeler gauge. Repair
the M/R blade if the edge void is within maximum repair damage limits
or replace the M/R blade with an airworthy M/R blade.
(v) If there is an edge void in a grip plate or doubler near the outboard
tip, tap inspect the affected area to determine the size and shape of
the void. Repair the M/R blade if the edge void is within maximum re-
pair damage limits or replace the M/R blade with an airworthy M/R
blade.
(vi) If there is any loose or damaged adhesive squeeze-out along any of
the bond lines, trim or scrape away the adhesive without damaging the
adjacent surfaces or parent material of the M/R blade. Determine if
there is an edge void or any corrosion by lightly sanding the trimmed
area smooth using 280 or finer grit paper. If there is no edge void
or corrosion, refinish the sanded area.
(vii) If there is an edge delamination along any of the bond lines or a
crack in the paint finish, determine if there is an edge void or a
crack in the grip pad, grip plate, doubler or skin by removing paint
from the affected area by lightly sanding in a spanwise direction
using 180-220 grit paper. If there are no edge voids and no cracks,
refinish the sanded area.
(viii) If any parent material is removed during any sanding or trimming in
paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD, repair the M/R
blade if the damage is within maximum repair damage limits or re-
place the M/R blade with an airworthy M/R blade.
(3) If there is a crack during any inspection in paragraph (e)(1) of this
AD, within 10 days after completing the inspection, report the infor-
mation requested in Appendix 1 to this AD by mail to the Los Angeles
ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount
Blvd., Lakewood, California 90712; attn. Galib Abumeri; or by email to
galib.abumeri@faa.gov.
(f) SPECIAL FLIGHT PERMITS
Special flight permits are prohibited.
(g) PAPERWORK REDUCTION ACT BURDEN STATEMENT
A federal agency may not conduct or sponsor, and a person is not re-
quired to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the re-
quirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 30 minutes per response, including the time for review-
ing instructions, completing and reviewing the collection of informa-
tion. All responses to this collection of information are mandatory.
Comments concerning the accuracy of this burden and suggestions for
reducing the burden should be directed to the FAA at: 800 Independence
Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)
(1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: Galib Abumeri, Aerospace Engineer
(Structures), Airframe Section, Los Angeles ACO Branch, Compliance and
Airworthiness Division, FAA, 3960 Paramount Blvd, Lakewood, California
90712; telephone 562-627-5324; email galib.abumeri@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating certificate
or under 14 CFR part 91, subpart K, we suggest that you notify your
principal inspector, or lacking a principal inspector, the manager of
the local flight standards district office or certificate holding dis-
trict office before operating any aircraft complying with this AD
through an AMOC.
(i) ADDITIONAL INFORMATION
HTC Service Notice No. 204-2100-1, dated July 5, 2017; Alert Service
Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013; Bell ASB No.
204-75-1 and Bell ASB No. 205-75-5, both Revision C and both dated
April 25, 1979, which are not incorporated by reference, contain
additional information about the subject of this AD. For service in-
formation identified in this AD, contact Bell Helicopter Textron, Inc.
PO Box 482, Fort Worth, TX 76101; telephone (817) 280-3391; fax (817)
280-6466; or at http://www.bellcustomer.com/files/. You may review
this service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX
76177.
(j) SUBJECT
Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on January 9, 2018. James A. Grigg, Acting
Director, Compliance & Airworthiness Division, Aircraft Certification Ser-
vice.
APPENDIX 1 TO AD 2018-02-08
Please report the following information by mail to the Los Angeles ACO
Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd.,
Lakewood, California 90712; attn. Galib Abumeri; or by email to galib.
abumeri@faa.gov.
(1) Date of inspection:
(2) Aircraft N-number:
(3) M/R blade serial number:
(4) M/R blade hours of time-in-service:
(5) Location of each crack:
(6) Dimension of each crack:
(7) Primary operating location of the M/R blade:
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer
(Structures), Airframe Section, Los Angeles ACO Branch, Compliance and
Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California
90712; telephone 562-627-5324; email galib.abumeri@faa.gov.
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